The Effects of Reynolds Number on Flow Separation of Naca Aerofoil

Authors

  • Muhammad Syahmi Abdul Hakim Department of Aeronautical, Automotive and Offshore Engineering, Fakulti Kejuruteraan Mekanikal, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
  • Mastura Ab Wahid Department of Aeronautical, Automotive and Offshore Engineering, Fakulti Kejuruteraan Mekanikal, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
  • Norazila Othman Department of Aeronautical, Automotive and Offshore Engineering, Fakulti Kejuruteraan Mekanikal, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
  • Shabudin Mat Department of Aeronautical, Automotive and Offshore Engineering, Fakulti Kejuruteraan Mekanikal, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
  • Shuhaimi Mansor Department of Aeronautical, Automotive and Offshore Engineering, Fakulti Kejuruteraan Mekanikal, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
  • Md. Nizam Dahalan Department of Aeronautical, Automotive and Offshore Engineering, Fakulti Kejuruteraan Mekanikal, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia
  • Wan Khairuddin Wan Ali Department of Aeronautical, Automotive and Offshore Engineering, Fakulti Kejuruteraan Mekanikal, Universiti Teknologi Malaysia, 81310 Skudai, Johor, Malaysia

Keywords:

UTM 2D aerofoil, wind tunnel experiments, flow visualization, flow separation

Abstract

The purpose of this study is to investigate the flow separation above UTM 2D Airfoil at three different Reynolds numbers which are 1 × 10  , 1.5 × 10  and 2 × 10  using pressure distribution method and flow visualization. The experiment was conducted in UTM-LST (Low Speed Tunnel). The pressure distribution is done on three different wing span, which are 40%, 50% and 70%m of span and was measured and plotted to observe the flow characteristic at angle of attack from 0° to 35° for all three different Reynolds numbers. The flow visualization method was done at 10m/s, 20m/s and 30m/s airspeed from 0° to 18°. It is concluded that the Reynolds number of 1 × 10  separates at 16°; Reynolds number of 1.5 × 10  separates at 18° and Reynolds number of 2 × 10  separates at 20°.

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Published

2020-12-01

How to Cite

Abdul Hakim, M. S. ., Ab Wahid, M. ., Othman, N. ., Mat, S. ., Mansor, S. ., Dahalan, M. N. ., & Wan Ali, W. K. . (2020). The Effects of Reynolds Number on Flow Separation of Naca Aerofoil. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 47(1), 56–68. Retrieved from https://www.akademiabaru.com/submit/index.php/arfmts/article/view/2229

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